1. Impact of Shock Wave Boundary Layer Interaction on the Internal Flow and Performance of Scramjet Intake.
- Author
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Kane, A. A., Peetala, R. K., and Kulkarni, V.
- Subjects
- *
SHOCK waves , *BOUNDARY layer equations , *SCRAMJET engines , *INTERNAL flows (Fluid mechanics) , *FRICTIONAL resistance (Hydrodynamics) , *MACH number - Abstract
The investigation of shock wave boundary layer interaction (SWBLI) and the prediction of the associated flow field and surface property variation are essential elements in designing scramjet engine. Therefore, the present study on SWBLI is carried out numerically on a two-dimensional scramjet intake model. The effect of various free-stream and wall conditions on the surface pressure, the skin friction coefficient and performance of the intake model are analysed. It is observed that increase in the Mach number and the free-stream temperature reduces the size of the separation zones within intake. The larger separation zones are observed by increasing the wall temperature. It is noted that the behaviour of SWBLI at ramp junction and isolator inlet are dissimilar and the ratio of free-stream stagnation temperature to wall temperature does not govern the parameter for separation bubble at isolator inlet. The present investigations recommend that the Mach number has significant influence while the wall temperature and the free-stream temperature have a little effect on the performance of the intake. [ABSTRACT FROM AUTHOR]
- Published
- 2021
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